Flying machine



' w.-o. CLARK Nov,- 22, 1927.

FLYING MACHINE Filed Feb. 13. "1925 2 Sheets-Sheet l Nov. 22, 1927.

W. D. CLARK FLYING MACHINE Filed Feb. 13. 1925 2 Sheets-Sheet 2 Patented Nov. 22, 1927.

1 entree I srATi-Es WiLLIAM DOUGLAS C AR or wAsnIne'romrrsTmc'r or cornivnarA;

- rrnrrne M'Aonmn Application filed February 13, .1925. Serial no 9,060.

This invention relates toirnprovements in flying machines and more particularly to the 1 i of fuel or movement of the-passengers and stabilizing means have been provided for this purpose. 7 g

It has been the usual practice to locate the adjusting screw in a'vertical position in the fuselage and apply theforce for moving the stabilizer at the rear spar. As the latter is usually more heavlly loaded than the front spar it is usuallyrequired to be externally braced. This bracing has to be carried on a lung post \VllBCil must be moved with the stabilizer; This adds to complication and weight. g

The present device is housed in the stabilizer and not in the fuselage in such a manner that it is self contained and may be removed with the stabilizer. The purpose is to provide a means of changing in flightthc angle which the stabilizer presents to the direction of air :fiow so that it may take a va' riable load to compensate for the shiftof. the center of gravity of the airplane due to,

the consumption of fuel, movement of passengers or any other condition that may change the trim of the airplane in flight.

ther objects will be in part obvious and in part hereinafter pointed out in theaccompanying drawings wherein is shown one of various possible embodiments of the invention and wherein corresponding parts are denoted by similar reference characters.

Figure 1 is a fragmentary plan of the.

tail of an airplane F1-gure2 1s a side elevatlon of the same .with parts of the outer surface broken away.

Figure 3 is. a vertical transverse section on the line 33 of Figure 2, showing the adjusting mechanism. r I

Figure 4 is a section on the line a r-4:301 Figure 3 showing one of the operating links.

Referring now tothe drawings in detail, 10 indicates the fuselage or tail portion of a flying machine or airplane provided with horizontal stabilizing surface 11 and vertical planes 12. Arudder 14 and pivoted horizontal planes 15 are provided and operated in the usual well-known manner. The stabilizer or horizontal plane 11 is provided with a rear'spar 16 parallel to the line of engagement" with. the horizontally pivoted I planes =orelevators 15. This spar, whichis mounted in the rear of the fuselage 10 provides a bearing to permit of rotary movement to serve as a center of rotation for the stabilizer; This construction also permits this rear spar to be. externally braced in the simplest manner and yet permit the forward .'end or edge'17 thereof to move up and down as andfwhen desired according to the shift of the center of gravity. Near this forward edge there is positioned av shaft 18 which is built into the stabilizer so' that it is free to rotate in'bearings 20 at its ends as shown clearly in Figure 1. This shaft is provided with right and left threads 21' as shown in Figure: 3 and is fitted at its center with a drum 22 so that the shaft may be rotated by wires 23 leading to the pilots position. Four threaded and trunnioned sleeves 24 coactfixed pivot points 26 as the shaft 18 is turned to cause the shaft and its associated construction to move either upwardly or down- .wardly two degrees as shown more clearly in Figure 2, for it will be clear. that as the I shaft 18 is rotated by means of the drum 22 the trunnion sleeves 24 will be moved towards orlfrom each other according to the direction of rotation. V v From the above it will be seen that if, for

example,the center of gravity of the machine should be moved aft due to consumption of fuel in the gas tank, it would be necessary to operate the compensating meansto cause a relative upward movement of the leading edge of the stabilizer whereby the craft will travel on a more even keel.

The mechanism is compact, self-contained and of the simplest construction and is believed to accomplish among others all of the What I claim is I 1. In an airplane, in combination, a horrzontal stabilizer hinged at its rear end and having its forward or leading edge free to be raised and lowered asdesired and means for accomplishing such adjustment during flight, said means including right and lefthand screw mechanism housed within the obiects and advantages herein set forth.

stabilizer surface.

2. In an airplane, in combination, an ad- Y justable stabilizer having a forward end free to move upwardly or downwardly and a hinged construction at its rear edge, means for causing such adjustment comprising a rotatable shaft mounted in said stabilizer and means operated from a distance for rotating said shaft in either direction.

3. In an airplane, in combination, an adjustable stabilizer having a forward end free to move upwardly or downwardly and a hinged construction at its rear edge, means for causing such adjustment comprising a rotatable shaft mounted in said stabilizer,

means operated from a distance for rotating 

